134
134

Jul 11, 2010
07/10

by
NON

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No Abstract Available

Topics: ANGULAR CORRELATION, ORBIT CALCULATION, TWO BODY PROBLEM, DISTANCE, ESTIMATES, INTERVALS

http://uf.catalog.fcla.edu/uf.jsp?st=UF003759947&ix=nu&I=0&V=D&pm=1

Topics: Body of revolution, Two-body problem, Aerodynamics, Unsteady flow (Aerodynamics.

This investigation was undertaken to determine the usefulness of interval analysis to numerical integration and matrix inversion techniques and to combine these results to determine the value of interval analysis in bounding computational errors in the two-body problem. Conclusions were that interval analysis may be worthwhile in certain small scale isolated problems, but its usefulness in any large scale problem is doubtful.

Topics: NASA Technical Reports Server (NTRS), CELESTIAL MECHANICS, NUMERICAL INTEGRATION, PROBLEM SOLVING,...

A reference handbook on modern dynamic orbit theory is presented. Starting from the most basic inverse-square law, the law of gravity for a sphere is developed, and the motion of point masses under the influence of a sphere is considered. The reentry theory and the orbital theory are discussed along with the relative motion between two bodies in orbit about the same planet. Relative-motion equations, rectangular coordinates, and the mechanics of simple rigid bodies under the influence of a...

Topics: NASA Technical Reports Server (NTRS), FLIGHT MECHANICS, ORBITAL MECHANICS, COORDINATES,...

3
3.0

Jul 17, 2016
07/16

by
NASA Technical Reports Server (NTRS)

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A converse theorem using Liapunov functions is used to obtain upper error bounds in optimal estimates of perturbed two body problems.

Topics: NASA Technical Reports Server (NTRS), ERROR ANALYSIS, ORBIT PERTURBATION, ORBITAL POSITION...

2
2.0

Jul 17, 2016
07/16

by
NASA Technical Reports Server (NTRS)

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Liapunov or energy restraint methods for dynamic stabilization in two body motion perturbation problems are considered. Results of computerized orbital stabilization estimates show that the application of energy restraint prevents the occurrence of consistent timing errors in the stepwise integration of equations of motion for a nearly circular orbit.

Topics: NASA Technical Reports Server (NTRS), EQUATIONS OF MOTION, NUMERICAL INTEGRATION, ORBIT...

368
368

Jun 21, 2010
06/10

by
Seelig, F. A

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Design and fabrication of flexible pivots for aerospace structures

Topics: COMPUTERIZED SIMULATION, INTERPLANETARY FLIGHT, DESCRIPTIVE GEOMETRY, FLIGHT SIMULATION, MARS...

193
193

Jul 26, 2010
07/10

by
Bioletti, Carlton; Cunningham, Bernard E

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No Abstract Available

Topics: INTERPLANETARY TRANSFER ORBITS, MARS PROBES, PARAMETER IDENTIFICATION, ROUND TRIP TRAJECTORIES,...

158
158

Jul 26, 2010
07/10

by
English, Roland D.; Carter, Howard S

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No Abstract Available

Topics: ORBIT CALCULATION, ORBITAL VELOCITY, ROTATION, SATELLITE INTERCEPTORS, ORBITAL MANEUVERS, ORBITAL...

755
755

Jun 21, 2010
06/10

by
SHARAF, SH. G., et al

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CORRECTION AND CALCULATION METHODS FOR SECOND AND FIRST ORDER PLUTONIAN PERTURBATIONS WITH RESPECT TO PERTURBING MASSES, AND NEW PLUTO ELEMENTS

Topics: INTERPLANETARY TRANSFER ORBITS, TWO BODY PROBLEM, ORBIT CALCULATION, ORBIT PERTURBATION, ORBITAL...

0
0.0

Jul 17, 2016
07/16

by
NASA Technical Reports Server (NTRS)

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A method developed to compute two-body, optimal, N-impulse trajectories was presented. The necessary conditions established define the gradient structure of the primer vector and its derivative for any set of boundary conditions and any number of impulses. Inequality constraints, a conjugate gradient iterator technique, and the use of a penalty function were also discussed.

Topics: NASA Technical Reports Server (NTRS), PRIMERS, VECTORS (MATHEMATICS), BOUNDARY CONDITIONS, BOUNDARY...

437
437

Sep 20, 2010
09/10

by
Wright, Willi

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The Shuttle Upper Atmosphere Mass Spectrometer (SUMS), a component experiment of the NASA Orbital Experiments Program (OEX), was flown aboard the shuttle Columbia (OV102) mounted at the forward end of the nose landing gear well with an atmospheric gas inlet system fitted to the lower fuselage (chin panel) surface. The SUMS was designed to provide atmospheric data in flow regimes inaccessible prior to the development of the Space Transportation System (STS). The experiment mission operation...

Topics: BETHE-SALPETER EQUATION, MATHEMATICAL MODELS, MOMENTUM, QUARKS, EFFECTS, EQUATIONS OF STATE,...

A preliminary analysis of the relative motion of a free flying experiment module in the vicinity of a space station under the perturbative effects of drag and earth oblateness was made. A listing of a computer program developed for determining the relative motion of a module utilizing the Cowell procedure is presented, as well as instructions for its use.

Topics: NASA Technical Reports Server (NTRS), FREE FLIGHT, SPACE STATIONS, SPACECRAFT MODULES, SPACECRAFT...

5,299
5.3K

Feb 18, 2010
02/10

by
MIT OpenCourseWare

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This course covers the fundamentals of astrodynamics, focusing on the two-body orbital initial-value and boundary-value problems with applications to space vehicle navigation and guidance for lunar and planetary missions, including both powered flight and midcourse maneuvers. Other topics include celestial mechanics, Kepler's problem, Lambert's problem, orbit determination, multi-body methods, mission planning, and recursive algorithms for space navigation. Selected applications from the...

Topics: space navigation, two body problem, boundary value problem, Kepler, astrodynamics, orbital...

The equations of motion and a computer program for the dynamics of a six degree of freedom body joined to a five degree of freedom body by a quasilinear elastic tether are presented. The forebody is assumed to be a completely general rigid body with six degrees of freedom; the decelerator is also assumed to be rigid, but with only five degrees of freedom (symmetric about its longitudinal axis). The tether is represented by a spring and dashpot in parallel, where the spring constant is a...

Topics: NASA Technical Reports Server (NTRS), DEGREES OF FREEDOM, DRAG DEVICES, TETHERLINES, TWO BODY...